Auxiliary jet power means for aircraft



June 24, 1947. .w ONEIL AUXILIARY JET POWER MEANS FOR AIRCRAFT Filed Sept. 30, 1944 4 Sheets-Sheet l INVENTOR. militia"; E OWeiL M rfiyl ATTORNEYS June 24, 1947. w. F. ONElL I AUXILIARY JET POWER MEANS FOR AIRCRAFT 4 Sheets-Sheet 2 Filed Sept. 50, 1944 INVENTOR. TViI/liam F- ONeil ATTOR June-24, 1947. I V w. F. ONEIL AUXILIARY'JET POWER MEANS FOR AIRCRAFT Filed Sept. 50 1944 4 Sheets-Sheet 3 INVENTOR. William ,F. ONeiL /h vw f-Xq,

ATTORNEY June 24, 1947. w. F. ONEIL AUXILIARY JET POWER MEANS FOR AIRCRAFT 4 Sheets-Sheet 4 Filed Sept. 50, 1944 INVENTOR. mlliam F'- ONeil ATTORNEY Patented June 24, 1947 AUXILIARY JET POWER MEANS FOR AIRCRAFT William F. ONeil, Akron, Ohio, assignor to The General. Tire & Rubber Company,

a corporation of Ohio Application September 30, 1944, Serial No. 556,558

. 3 Claims.

This invention relates to auxiliary propulsion devices for airplanes and its mainobjects are to provide an improved system of propulsion jets by which the speed of travel of a. plane may be momentarily accelerated during take-offs, and to provide jets so mounted and so arranged that they may be utilized for quickly reducing speed to facilitate the landing, braking or retarding action of the plane.

A further object of the invention is to provide a mounting fo a propulsion jet nozzle by means of which the nozzle may be retracted into the body of the plane when not in use and extended to an operative position outside the body of the plane.

A further object is to provide nozzles that are adjustable from a forwardly directed position to a rearwardly directed position so that they may be used either for retarding or accelerating the speed of travel.

An additional'object of the invention is to provide jet controlling means for preventing operation of the jet when it is in any position other than, the extended operative position.

With the above and other objects in view, the invention may be said to comprise the device as illustrated in the accompanying drawings, hereinafter described and particularly set forth in appended claims, together with such variations and modifications thereof as will be apparent to one skilled in the art to which the invention pertains.

Reference should be had to the accompanying drawings forming a part of this specification, in which Fig. 1 is a top plan view of an airplane to which the invention is to be applied;

Fig. 2 is a section taken on the line indicated at2-2 inFig.1; 4

Fig. 3 is a section taken on the line indicated at 33 in Fig. 2;

Fig. 4 is a diagrammatic view showing the tanks for the jet creating fluids and the connections from the tanks to the forwardly directed jets on the tail planes;

Fig. 5 is a fragmentary plan view on an enlarged scale of one of the jet nozzles mounted upon a fuselage;

Fig. 6 is a side elevation of the jet nozzle shown in Fig. 5; t

Fig. 7 is a vertical section taken on the line indicated at 1-'I in Fig. -6;

Fig. 8 is a vertical section taken on the line indicated at 8- 8 in Fig. '7; l

Akron, Ohio,

Fig. 9 is a horizontal section taken on the line indicated at 5-9 in Fig. '7;

Fig. 10 is a vertical section taken on the line indicated at Ill-l 0 in Fig. 7

Fig, 11 is a diagrammatic view of the fluid pressure tanks and connections from the tanks to the fuselage nozzles;

Fig. 12 is a fragmentary top plan view showing a modified form of adjustable mounting for the fuselage nozzles Fig. 13 is a section taken on theline indicated at l3--|3 in Fig. 12, and

Fig. 14 is a section taken on the line indicated at 14-4-4 in Fig. 13.

In the accompanying drawings the invention is shown applied to an airplane which has a fuse lage I, wings 2, a rudder 3 at the rear end of the fuselage, elevators 4 on opposite sides of the rudder, and tail planes 5 rigid with the fuselage forwardly of the elevators. The wings 2 are shown provided with rearwardly directed propulsion nozzles 6 that are mounted in the trailing edges of the wings. Jet creating fluids may be delivered tov the nozzles 6 from cylinders 1 through suitable connections (not shown). The jet may be, created in each nozzle by means of two fluids, one of which is a combustible composition delivered from one of the tanks and the other of which is an oxidizing composition delivered fromthe other tank, the two fluids uniting when delivered into the nozzle to cause combustion and extremely rapid expansion of gases, whichcreates a propulsion jet. The igniting fluid is preferably one which carries sufficient oxygen to support combustion of the fluid fuel. For example, the igniting fluid may be fuming nitric acid and the fluid fuel may be aniline. Where compositions are employed which do not spontaneously ignite when mixed, suitable devices may be provided for igniting the mixture.

Propulsion jets produced by rockets or by means of nozzles similar to the nozzles 6 have been provided for assisting in the take-01f of airplanes. The present invention, however, contemplates the use of such jets for retarding the forward speed of an airplane, as well as for increasing the acceleration during take-offs.

As shown in Fig. 1, a plurality of forwardly directed nozzles 8. are mounted in the leading edges of the tail planes 5 and these nozzles are connected to fluid pressure cylinders 9 and lilv which supply the jet creating fluids. As shown in Fig. 4, cylinders Sand iii are connected through valves II and [2 with headers l3 and I4, and each of the nozzles 8 is provided with pipes l5 and I6 which lead to the headers I3 and [4, respectively. Any suitable and convenient means may be employed for operating the valves I l and I2 to create propulsion jets in the nozzles 8 when desired. The action of the jets created in the nozzles 8 offers a strong resistance to forward movement which is effective to quickly reduce the forward speed. Such retardation of forward speed is highly desirable to enable an airplane to land on a short runway.

In addition to the rearwardly directed nozzles 6 and the forwardly directed nozzles 8, additional jet nozzles I! are mounted upon the fuselage l in the space between the wings 2 and the tail planes 5. Each nozzle [1 is supplied with jet creating fluids from a pair of pressure cylinders l8 and I3. Delivery of fluid from the cylinders l8 and I9 is controlled by valves 20 and 2|, these valves controlling the flow to the pipes 22 and 23 through which the fluid from the cylinders I6 and I9 is delivered to the nozzles l1.

As shown in Fig. 1, two nozzles H are provided, one on each side of the fuselage. The two nozzles H are identical and each may be supplied from an independent pair of fluid pressure cylinders. Figs. to show the mounting of one of the nozzles ll, it being understood that the other nozzle is mounted in identical manner on the opposite side of the fuselage. Each nozzle H is supported on a carrier arm 24 that is mounted to turn about the axis of a pivot shaft 25 which extends longitudinally of the fuselage. The shaft 25 is mounted inside the fuselage and each side wall of the fuselage is provided with an opening 26 through which the nozzle I! may be moved from a retracted position within the fuselage, to its operative position outside the fuselage by a pivotal movement of the arm 24.

An arm 21 attached to the arm 24 carries a closure plate 28 which is adapted to close the opening 26 when the nozzle is swung to its retracted position shown in dotted lines in Fig. 7.

The arm 24 has a bearing portion 29 at its outer end on which a tubular nozzle supporting member 36 is rotatably mounted. The axis of the tubular member 36 is disposed transversely with respect to the axis of the shaft 25, and the member 36 is rotatable to position the nozzle I! to direct a jet forwardly or rearwardly as may be desired. The member 30 has a nozzle supporting cap 3| at its outer end to which the nozzle I! is secured by means of a clamping plate 32 secured to the cap 3| by means of screws 33. The nozzle I! is provided with shoulders 34 and 35 which engage opposite sides of the clamping portion of the cap 3| so that the nozzle is firmly held against endwise movements.

A worm gear 36 is fixed in the inner end of the tubular member 30 and meshes with a worm 31 fixed to a shaft 38 that is driven through reduction gears 39 and 46 by an electric motor 4|. By operating the motor 4| the position of the nozzle I! may be reversed when desired.

For shifting the nozzle into or out of the fuselage, a fluid pressure cylinder 42 is pivoted at its upper end to the fuselage and has a piston rod 43 that is pivoted to an arm 44 attached to the shaft 25. The usual means may be provided for controlling the delivery of fluid under pressure to the cylinder 42 so that the nozzle may be moved from the position shown in full lines in Fig. 7 to the position shown in dotted lines, or vice versa, and held in either adjusted position.

As shown in Fig. 10, the shaft 25 has a tubular body portion and is rotatably mounted in fixed bearing members 45. A plug 46 closes one end of the shaft 25 and extends beyond the tubular portion. The plug 46 is provided with an axial passage 41 leading from its inner end and extending 5 to a radial passage 48 beyond the end of the tubular portion of the shaft. A collar 49 is mounted upon the plug 46 and is held against turning movements by means of a pin 50 which connects the same to the adjacent fixed bearing member 45. The collar 49 has a radial passage 5| that is adapted to register with the radial passage 48 in the plug 46 when the arm 24 is in upright position, and the pipe 22 is attached to the collar 49 and communicates with the radial passage 5 I. A pipe 52 is attached to the inner end of the passage 41 and extends through the wall of the tubular shaft 25 to a collar 53 that is mounted on the tubular member 39. The tubular member 36 has a core member 54 attached thereto which provides a bearing for the collar 53. The collar 53 has a radial pasage 55 that communicates with the pipe 52 and which is adapted to register with one or the other of two transverse passages 56 and 51 in the core member 54. The passages 56 and 5! are angularly spaced and communicate with an axial passage 58 which communicates through the cap 3| with a pipe 59 leading from the cap to the nozzle Ill.

The plug 46 and collar 49 form a valve controlling the fiow of fluid to the nozzle, the radial passage 48 of the plug 46 attached to the shaft 25 being so positioned that communication is established with the supply pipe 22 only when the carrier arm 24 is positioned to support the nozzle ll outside the fuselage, as shown in full lines in Fig. 7. The core member 54 and collar 53 form a second valve in which the passages 55 and 51 of the core member 54 are so positioned that fluid is delivered to the nozzle l1 through the pipe 52 only when the nozzle I1 is directed forwardly or rearwardly, the two passages 56 and 51 being spaced 180.

The core 54 is provided with a second axial passage 69 that extends to the cap 3| and com- 45 municates with the supply pipe 23,'which is in the form of a flexible hose and positioned to permit the turning of the tubular member 30 through an angle of 180 to adjust the nozzle [1. The passage 60 is connected to the nozzle I! through a short pipe 6| extending from the cap 3| to the nozzle H. The nozzles I! may be used in conjunction with the nozzles 6 to increase acceleration during take-offs, or they may be used 55 alone or in conjunction with the nozzles 8 on the tail planes 5 to retard the speed of the plane when landing. v

In Figs. 12 to 14 of the drawings, a modified mounting of fuselage nozzles is disclosed in which 60 nozzles '62 are attached to the ends of arms 63 that are formed integral with a central cap 64 that is fixed to the upper end of a rotatable post 65 that is mounted in a bearing member 66,

mounted centrally of the fuselage on a cross 65 beam 61. The two arms 63 are preferably diametrically alined and of equal length so that When the supporting post 65 is rotated the nozzles may be swung from the retracted inoperative position shown in dotted lines in Fig. 12, either to a forwardly directed operative position as shown in full lines in Fig. 12, or to a rearwardly directed operative position such as shown in dotted lines in Fig, 12. I

For imparting turning movements to the post 65, a worm gear 68 is attached to the lower end of the post and meshes with a worm 69 that is adapted to be driven by a motor 10.

Jet creating fluids may be delivered to the nozzles 62 through flexible pipes H connected to the cap 64 and through pipes 1.2 connected to the cap 64 and extending through the hollow arm 63 to the nozzles 62. The fuselage is provided with openings 13 on opposite sides thereof through which the arms 63 and nozzles 62 may be moved, and these openings may be closed by suitable doors 14 when the nozzles and end supporting arms are positioned in the fuselage as shown in dotted lines in Fig. 12.

It is to be understood that variations and modifications of the specific device herein shown and described for purposes of illustration, may be made without departing from the spirit of the invention.

What I claim is:

1. In an airplane having wings and a fuselage, a jet nozzle mounted on the fuselage for movement from a retracted position within the fuselage to an operative position outside the fuselage, means for supplying fuel to said nozzle, and means for automatically rendering said fluid supplying means inoperative when the nozzle is moved to retracted position.

2. An airplane having a chamber, a jet nozzle mounted on said airplane for movement from a retracted position within said chamber to an operative position outside said chamber, means for creating a propulsion jet in said nozzle and means for automatically rendering said jet creating means inoperative when said nozzle is moved to retracted position.

3. In an airplane, an arm mounted for movement about an axis transverse to the arm, a jet creating combustion nozzle mounted on the arm for angular adjustment about an axis transverse to the arm and to said first mentioned axis, a tank containing fluid under pressure, and means for conducting fluid from said tank to said nozzle, including valves controlled by pivotal movements of said arm and of said nozzle.

WILLIAM F. O .lIL.

REFERENCES CITED The following references are of record in the file of this patent:

UNITED STATES PATENTS 

